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A two-stage radial swirler for a gas turbine combustor

A gas turbine and swirler technology, applied in combustion chambers, combustion methods, combustion equipment, etc., can solve the problems of smaller load adjustment range, poor combustion stability, combustion oscillation, etc., to prevent backfire, stabilize combustion, and expand regulation. range effect

Active Publication Date: 2021-01-29
DONGFANG TURBINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But at the same time, due to the transformation of the combustion mode, it also brings a series of challenges to the design of the burner, such as poor combustion stability, flashback, narrowing of the load adjustment range, combustion oscillation, etc.

Method used

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  • A two-stage radial swirler for a gas turbine combustor
  • A two-stage radial swirler for a gas turbine combustor
  • A two-stage radial swirler for a gas turbine combustor

Examples

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Effect test

Embodiment 1

[0039] Such as figure 1 As shown, a gas turbine combustor two-stage radial swirler in this embodiment:

[0040] A two-stage radial swirler for a gas turbine combustor, comprising a first-stage radial swirler 1 and a second-stage radial swirler 2;

[0041] Both the first-stage radial swirler 1 and the second-stage radial swirler 2 include a radial swirler and a guide ring and a premixing chamber arranged downstream of the airflow, and the guide ring is located in the radial swirl Between the swirler and the premixing chamber, the radial swirler and the premixing chamber are connected;

[0042] The radial swirler includes a plurality of swirl blades arranged in a circle, the top of the swirl blades is fixedly connected with a circular end plate, and a concentric central hole is arranged on the circular end plate; the swirl blades extend radially A swirl channel extending along the tangential direction of the center hole is formed between adjacent swirl blades, the swirl chann...

Embodiment 2

[0054] Such as figure 2 As shown, a gas turbine combustor two-stage radial swirler in this embodiment:

[0055] A two-stage radial swirler for a gas turbine combustor, comprising a first-stage radial swirler 1 and a second-stage radial swirler 2;

[0056] Both the first-stage radial swirler 1 and the second-stage radial swirler 2 include a radial swirler and a guide ring and a premixing chamber arranged downstream of the airflow, and the guide ring is located in the radial swirl Between the swirler and the premixing chamber, the radial swirler and the premixing chamber are connected;

[0057] The radial swirler includes a plurality of swirl blades arranged in a circle, the top of the swirl blades is fixedly connected with a circular end plate, and a concentric central hole is arranged on the circular end plate; the swirl blades extend radially A swirl channel extending along the tangential direction of the center hole is formed between adjacent swirl blades, the swirl chan...

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Abstract

The invention discloses a two-stage radial swirler for a gas turbine combustor, which belongs to the technical field of gas turbines. A two-stage radial swirler for a gas turbine combustor of the present invention includes a first-stage radial swirler and a second-stage radial swirler, and a first-stage radial swirler and a second-stage radial swirler The flow device includes a radial swirler and a guide ring and a premixing chamber arranged downstream of the air flow. The guide ring is located between the radial swirler and the premixing chamber, and communicates with the radial swirler and the premixing chamber. , the bottom of the swirl vane of the second-stage radial swirler is connected to the circular end plate of the first-stage radial swirler. Adopting the double-stage radial swirler of a gas turbine combustor of the present invention can realize stable combustion, prevent flashback, and suppress combustion oscillation, and supply fuel in stages at low loads, expanding the adjustment and adjustment of the gas turbine range, which is more conducive to stable combustion.

Description

technical field [0001] The invention relates to a gas turbine part, in particular to a two-stage radial swirler for a gas turbine burner, belonging to the technical field of gas turbines. Background technique [0002] Dry low NOx (DLN) combustion technology (DLN) is a mature technology commonly used by heavy-duty gas turbines in the world to control pollutant emissions. In dry low NOx combustion technology, the most critical is to achieve uniform mixing of fuel and air and dilute phase premixed combustion. The most essential advantage of dilute-phase premixed combustion is its low flame temperature, which directly affects the formation of NOx. But in addition to controlling the ratio of fuel to air, the level of NOx production is also very sensitive to the degree of fuel-air mixing uniformity the system can achieve. Mixing air and fuel evenly through a swirler is the most commonly used method in practice. [0003] Compared with traditional diffusion combustors, DLN techno...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38
Inventor 凤云仙田晓晶冯珍珍杨安建张渊刘维兵孔祥林吴文彭艾松
Owner DONGFANG TURBINE CO LTD
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